Abstract: This disclosure describes a cooling enhancement for gas turbine engine outer air seals. The invention provides heat transfer using impingement cooling and convective cooling through the use of tortuous cooling air passages, and film effective film cooling through the use of cooling air discharge slots that are oriented so as to discharge coolant into the working fluid flowpath with a minimum of momentum exchange between the cooling air and the working fluid.

Abstract: This disclosure describes a cooling and manufacturing enhancement for gas turbine engine outer air seals. The invention provides convective cooling in a counter-flow array, internal heat transfer augmentation through the use of boundary layer trip-strips, coolant Mach number control through the use of tapered convective channels, inter-segment purge without additional secondary cooling air, and is castable.

Abstract: A cooling enhancement for a gas turbine engine blade outer air seal is made up of a plurality of arcuate seal segments, and each one has one or more internal cooling passages. Each segment has a supply surface opposite and in spaced relation to a sealing surface, and first and second end surfaces extending from the sealing surface to the supply surface. Each of the end surfaces includes a substantially planar perpendicular surface and a substantially planar canted surface intersecting at an included angle of between 100 degrees and 140 degrees, and the supply surface has a plurality of cooling orifices adjacent the second end surface. At least one cooling passage extends from the first end surface towards the second end surface, and each cooling passage intersects the first end surface and terminates short of the second end surface. Each cooling passage communicates with the supply surface through at least one of the cooling orifices.

Abstract: The present invention is a brush seal for use between two components which move relative to each other. The brush seal has multiple layers of bristles, and the bristles within a particular layer have the same cross-sectional area or "thickness". The layers are arranged in the order of increasing thickness, with the bristles of the layer that forms the high pressure face of the brush seal having the smallest cross-sectional area. The larger bristles support the smaller bristles, and a backing plate supports the larger bristles.

Abstract: In a gas turbine engine a novel method and apparatus that measures axial thrust loads in engine bearings is characterized by a controller which dynamically selects axial loads on an engine thrust bearing by varying internal gas pressures in bearing trim cavities in accordance with a predetermined schedule.

Abstract: A method is disclosed of removing a plurality of rim blade dies around the circumference of a disc while the disc, blades and blade dies are at a temperature approximating those during the forging operation. The upper disc forming die is removed along with a restraining back-up member around the rim blade dies and the rim blade dies are forced radially outwardly to prevent interference between the blade dies and blades during their cool down period. A blade die removal tool has a plurality of individual radial arms extending outwardly from a central hub. The free ends of the arms engage the blade dies and the ram of the press moves the central hub downwardly to move the blade dies radially outwardly.